CN107483230B - Ground detection method for airplane wheel-borne signals - Google Patents
Ground detection method for airplane wheel-borne signals Download PDFInfo
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- CN107483230B CN107483230B CN201710618160.6A CN201710618160A CN107483230B CN 107483230 B CN107483230 B CN 107483230B CN 201710618160 A CN201710618160 A CN 201710618160A CN 107483230 B CN107483230 B CN 107483230B
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- 238000001514 detection method Methods 0.000 title claims abstract description 63
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 238000013024 troubleshooting Methods 0.000 abstract description 12
- 238000000034 method Methods 0.000 abstract description 10
- 230000005283 ground state Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L41/00—Arrangements for maintenance, administration or management of data switching networks, e.g. of packet switching networks
- H04L41/06—Management of faults, events, alarms or notifications
- H04L41/0677—Localisation of faults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
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Abstract
The invention discloses a ground detection method for aircraft wheel-borne signals, and belongs to the technical field of signal detection. The method comprises the step of connecting detection equipment with a wheel-mounted signal receiving and releasing control unit, wherein the detection equipment comprises a plurality of wheel-mounted signal receiving units and a display unit, the plurality of wheel-mounted signal receiving units correspond to a plurality of wheel-mounted signal receiving systems one by one, and the display unit is used for displaying the signal receiving condition of the wheel-mounted signal receiving units. The ground detection equipment for the aircraft wheel-borne signals can be used for quickly positioning and eliminating the wheel-borne signal faults. Because the airplane spare parts are not needed to replace equipment on the airplane to position faults, the ground detection equipment for the wheel-borne signals can be conveniently applied to the troubleshooting process of the wheel-borne signals, has certain universality for airplane system users of all the wheel-borne signals, and can obviously shorten the troubleshooting time.
Description
Technical Field
The invention belongs to the technical field of signal detection, and particularly relates to a ground detection method for an aircraft wheel-borne signal.
Background
A landing gear control system of a military and civil aircraft can provide a hard wire wheel-mounted signal in a ground/open mode, wherein the ground is used for indicating that the aircraft is in a grounding state, and the open is used for indicating that the aircraft is in an air state. Many systems on the aircraft acquire the wheel-mounted signals for realizing the system control function, for example, the brake control unit performs ground brake control by acquiring the wheel-mounted signals, the ground proximity warning device performs warning triggering by acquiring the wheel-mounted signals, and the like, and the wheel-mounted signals increasingly become a common information source of the aircraft.
Once the wheel-mounted signal fails, the functions of various systems of the airplane are abnormal, so that the airplane cannot fly off. The existing common ground fault elimination method is to replace a retraction control unit or a wheel-borne signal receiver of an undercarriage control system of a wheel-borne signal sender, and the method is also used for eliminating one wheel-borne signal fault, but when a plurality of wheel-borne signal paths are in fault, the difficulty and the workload are multiplied, and how to quickly position and eliminate the wheel-borne signal fault becomes a new problem.
Disclosure of Invention
In order to solve the problems, the invention provides the airplane wheel load signal ground detection equipment, when the airplane is in a ground state, the airplane wheel load signal ground detection equipment is connected to a detection interface of a retraction control unit, and a wheel load signal path with a fault is quickly and accurately positioned under the condition that airborne equipment on the airplane is not replaced.
The detection process of the airplane airborne signal ground detection equipment mainly comprises the following steps: connecting detection equipment with a wheel-mounted signal receiving and releasing control unit, wherein the detection equipment comprises a plurality of wheel-mounted signal receiving units and a display unit, the plurality of wheel-mounted signal receiving units correspond to a plurality of wheel-mounted signal receiving systems one by one, and the display unit is used for displaying the signal receiving condition of the wheel-mounted signal receiving units;
if the wheel-mounted signal collected by any wheel-mounted signal receiving system is always in a grounding state, then:
step 11, enabling the airplane wheel-borne signals to be in an air state;
step 12, reading the signal receiving condition of the display unit of the detection equipment;
step 13, if the wheel-borne signals collected by the detection equipment are all in a grounding state, judging that the wheel-borne signal receiving and releasing control unit has a fault, if the wheel-borne signals collected by the detection equipment are partially in the grounding state, judging that the output channel of the wheel-borne signal receiving and releasing control unit corresponding to the grounding state has the fault, and if the wheel-borne signals collected by the detection equipment are in an air state, judging that the wheel-borne signal receiving system corresponding to the air state has the fault;
if the wheel-borne signals collected by any wheel-borne signal receiving system are always in the air state, the following steps are carried out:
step 21, confirming that the airplane wheel load signal is in a ground state;
step 22, reading the signal receiving condition of the display unit of the detection equipment;
and 23, if the wheel-mounted signals acquired by the detection equipment are all in an air state, judging that the wheel-mounted signal receiving and releasing control unit has a fault, if the wheel-mounted signals acquired by the detection equipment are in an air state, judging that an output channel of the wheel-mounted signal receiving and releasing control unit corresponding to the air state has a fault, and if the wheel-mounted signals acquired by the detection equipment are in a grounding state, judging that a wheel-mounted signal receiving system corresponding to the grounding state has a fault.
Preferably, the wheel-mounted signal receiving system at least comprises a brake control unit, a traffic warning and collision avoidance unit, a flight control computer, an environment control unit, a weather radar, an engine control device and a data acquisition computer.
Preferably, in step 11, the airplane is jacked up by using a jack, so that the airplane wheel-borne signal is in an air state.
The invention can quickly locate and eliminate the wheel load signal fault through the airplane wheel load signal ground detection equipment. Because the equipment on the airplane does not need to be replaced, the detection equipment can be conveniently applied to the troubleshooting process of the wheel-borne signals, and the troubleshooting time can be obviously shortened.
Drawings
Fig. 1 is a schematic diagram of the detection principle of a preferred embodiment of the ground detection device for airborne signal according to the present invention.
Fig. 2 is a block diagram of a wheel-mounted signal receiving system according to the embodiment of the present invention shown in fig. 1.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
The airplane wheel-borne signal ground detection equipment is generally used for airplane ground troubleshooting under the condition of wheel-borne signal failure. In the troubleshooting process, when the airplane is parked on the normal ground, the simulated airplane wheel load is in a grounding state, and when the airplane is jacked up by the jack, the simulated airplane wheel load is in an air state.
When a user of the wheel load system on the airplane collects wheel load signals sent by the retraction control unit, the wheel load signals are hard line signals in a ground/open mode, the ground is used for representing that the airplane is in a grounding state, and the open is used for representing that the airplane is in an air state. The users of the wheel-borne system usually have a fault state of receiving no grounding state or receiving no air state in the process of using the wheel-borne signals.
When the wheel-load signals collected by a certain wheel-load system user are always in a grounding state and cannot be received in the air, the troubleshooting scheme is as follows:
1) jacking the airplane by using a jack, confirming that the airplane wheel load signal is in an air state, disconnecting a power supply of a retraction control unit on the airplane and a wheel load system user with a fault, and directly connecting a detection port of the retraction control unit with airplane wheel load signal ground detection equipment;
2) supplying power to the retraction control unit, confirming that a failed wheel load system user does not supply power, switching on the power supply of the airplane wheel load signal ground detection equipment, and if the wheel load signal acquired by the airplane wheel load signal ground detection equipment is in a grounding state, confirming that the retraction control unit has a fault; and if the wheel load signal acquired by the airplane wheel load signal ground detection equipment is in an air state, the user fault of the wheel load system can be confirmed.
When the wheel load signal collected by a certain wheel load system user is always in an on state and cannot be received in a grounding state, the troubleshooting scheme is as follows:
1) confirming that the airplane is in a normal ground parking state, disconnecting a power supply of a retraction control unit on the airplane and a wheel load system user with a fault, and directly connecting a detection port of the retraction control unit with airplane wheel load signal ground detection equipment;
2) supplying power to the retraction control unit, confirming that a failed wheel load system user does not supply power, switching on the power supply of the airplane wheel load signal ground detection equipment, and if the wheel load signal acquired by the airplane wheel load signal ground detection equipment is in an on state, confirming that the retraction control unit fails; and if the wheel load signal acquired by the airplane wheel load signal ground detection equipment is in a ground state, the user fault of the wheel load system can be confirmed.
The brake control unit is used as a wheel load signal receiving party, and the specific implementation process is as follows:
in case 1, when the wheel-mounted signal collected by the brake control unit is always in a grounded state and cannot be received in the air, the troubleshooting steps are as follows:
1) as shown in fig. 1, the airplane is jacked up by a jack, the airplane wheel load signal is confirmed to be in an air state, a switch K1, a switch K2 and a switch K3 are disconnected, and the detection port of the retraction control unit is connected to airplane wheel load signal ground detection equipment according to fig. 1;
2) the switch K3 is opened, the switch K2 is closed, the switch K1 is closed, and if the wheel-borne signals collected by the airplane wheel-borne signal ground detection equipment are in a grounding state, the failure of the retraction control unit can be confirmed; if the wheel-borne signals collected by the airplane wheel-borne signal ground detection equipment are in an air state, the brake control unit can be confirmed to be in a fault state.
In case 2, when the wheel load signal collected by the brake control unit is always in an on state and cannot be received in a grounding state, the troubleshooting steps are as follows:
1) confirming that the airplane is in a ground state, disconnecting a switch K1, a switch K2 and a switch K3, and connecting a detection port of a retraction control unit to airplane wheel-mounted signal ground detection equipment according to the figure 1;
2) the brake control unit is disconnected with the switch K3, the switch K2 is closed, the switch K1 is closed, and if the wheel-mounted signals collected by the airplane wheel-mounted signal ground detection equipment are in a grounding state, the brake control unit can be confirmed to be in a fault state; if the wheel load signal collected by the airplane wheel load signal ground detection equipment is in an on state, the failure of the retraction control unit can be confirmed.
In addition to the brake control unit, the ground detection equipment for the airborne signals of the invention comprises a plurality of paths of airborne signal receiving units and a display unit, wherein the plurality of paths of airborne signal receiving units are correspondingly connected with a plurality of airborne signal receiving systems one by one and can be further connected at one time, and the plurality of airborne signal receiving systems are used for detecting, as shown in figure 2, the airborne signal receiving systems at least comprise a brake control unit, a traffic warning and collision avoidance unit, a flight control computer, an environment control unit, a weather radar, an engine control device and a data acquisition computer.
The invention has the advantages and beneficial effects that: the invention quickly locates and eliminates the wheel load signal fault through the airplane wheel load signal ground detection equipment shown in figure 1. Because the equipment on the airplane does not need to be replaced, the device can be conveniently applied to the wheel-borne signal troubleshooting process, and the troubleshooting time can be obviously shortened.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (3)
1. A ground detection method for aircraft wheel-borne signals is used for detecting a wheel-borne signal receiving and releasing control unit and a plurality of wheel-borne signal receiving systems respectively connected with the wheel-borne signal receiving and releasing control unit, and is characterized by comprising the following steps:
connecting detection equipment with a wheel-mounted signal receiving and releasing control unit, wherein the detection equipment comprises a plurality of wheel-mounted signal receiving units and a display unit, the plurality of wheel-mounted signal receiving units correspond to a plurality of wheel-mounted signal receiving systems one by one, and the display unit is used for displaying the signal receiving condition of the wheel-mounted signal receiving units;
if the wheel-mounted signal collected by any wheel-mounted signal receiving system is always in a grounding state, then:
step 11, enabling the airplane wheel-borne signals to be in an air state;
step 12, reading the signal receiving condition of a display unit of the detection equipment;
step 13, if the wheel-borne signals collected by the detection equipment are all in a grounding state, judging that the wheel-borne signal receiving and releasing control unit has a fault, if the wheel-borne signals collected by the detection equipment are partially in the grounding state, judging that the output channel of the wheel-borne signal receiving and releasing control unit corresponding to the grounding state has the fault, and if the wheel-borne signals collected by the detection equipment are in an air state, judging that the wheel-borne signal receiving system corresponding to the air state has the fault;
if the wheel-borne signals collected by any wheel-borne signal receiving system are always in the air state, the following steps are carried out:
step 21, confirming that the airplane wheel-borne signal is in a grounding state;
step 22, reading the signal receiving condition of the display unit of the detection device;
and 23, if the wheel-mounted signals acquired by the detection equipment are all in an air state, judging that the wheel-mounted signal receiving and releasing control unit has a fault, if the wheel-mounted signals acquired by the detection equipment are in an air state, judging that an output channel of the wheel-mounted signal receiving and releasing control unit corresponding to the air state has a fault, and if the wheel-mounted signals acquired by the detection equipment are in a grounding state, judging that a wheel-mounted signal receiving system corresponding to the grounding state has a fault.
2. The ground detection method for the wheel-borne signals of the airplane as claimed in claim 1, wherein the wheel-borne signal receiving system at least comprises a brake control unit, a traffic alarm collision avoidance unit, a flight control computer, an environment control unit, a weather radar, an engine control device and a data acquisition computer.
3. The ground detection method for the aircraft wheel-borne signal according to claim 1, characterized in that in the step 11, the aircraft is jacked up by using a jack, so that the aircraft wheel-borne signal is in an air state.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710618160.6A CN107483230B (en) | 2017-07-26 | 2017-07-26 | Ground detection method for airplane wheel-borne signals |
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| CN201710618160.6A CN107483230B (en) | 2017-07-26 | 2017-07-26 | Ground detection method for airplane wheel-borne signals |
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| CN107483230B true CN107483230B (en) | 2020-11-03 |
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| CN112731036B (en) * | 2020-12-25 | 2024-06-18 | 武汉航空仪表有限责任公司 | Main rotor heating fault detection system and detection method for rotor deicing system |
| CN114408190A (en) * | 2021-12-29 | 2022-04-29 | 陕西千山航空电子有限责任公司 | Throwing control module state detection circuit and throwing type recorder |
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| CN102753435A (en) * | 2010-03-18 | 2012-10-24 | 三菱重工业株式会社 | Aerodynamic coefficient estimation device and control surface failure/damage detection device |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6564142B2 (en) * | 1999-02-01 | 2003-05-13 | Aero Modifications & Consulting, L.L.C. | System and apparatus for determining the center of gravity of an aircraft |
| CN105523177A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft brake ground protection system and method thereof |
| CN104494815B (en) * | 2014-11-18 | 2016-06-01 | 西安航空制动科技有限公司 | A kind of Aircraft Anti-skid Break Control lands protection method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102753435A (en) * | 2010-03-18 | 2012-10-24 | 三菱重工业株式会社 | Aerodynamic coefficient estimation device and control surface failure/damage detection device |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
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